引用本文: 蒋献, 孟敏, 石海波等. 返力连杆作动器驱动的舵面铰链力矩飞行实测模型. 力学与实践, 2022, 44(6): 1342-1350.
Jiang Xian, Meng Min, Shi Haibo, et al. Rudder hinge moment flight measurement model driven by reaction link actuator. Mechanics in Engineering, 2022, 44(6): 1342-1350.
 Citation: Jiang Xian, Meng Min, Shi Haibo, et al. Rudder hinge moment flight measurement model driven by reaction link actuator. Mechanics in Engineering, 2022, 44(6): 1342-1350.

## RUDDER HINGE MOMENT FLIGHT MEASUREMENT MODEL DRIVEN BY REACTION LINK ACTUATOR

• 摘要: 在返力连杆作动器驱动的某型民机方向舵铰链力矩飞行实测中，已有的铰链力矩测量方法需同时测量返力杆轴/垂向实测载荷和作动筒轴向载荷，但由于结构空间限制，作动筒上无法加装应变电桥，测载难度大。本文提出了一种仅需测量与舵面无连接的小连杆轴向载荷即可间接反算舵面铰链力矩的模型，利用有限元方法确定了小连杆的应变测载位置，采用脱机载荷校准试验和铰链力矩联机验证试验建立并验证了舵面铰链力矩实测模型，通过协调侧滑飞行试验得到了方向舵铰链力矩实测结果。分析结果表明该实测模型结果准确有效，满足试飞要求，可用于类似驱动结构的舵面铰链力矩测量。

Abstract: In order to solve the problem of rudder hinge moment flight measurement of a civil aircraft driven by reaction link actuator, the presently available hinge moment measurement method needs to simultaneously measure the axial/vertical load of actuator and the axial load of small connecting rod. However, due to the limitation of structural space, the strain bridge cannot be installed on the actuator, so the load measurement is difficult. In this paper, a novel model is proposed to calculate the hinge moment of the rudder indirectly by measuring the axial load of the small connecting rod which is not connected to the rudder surface. Firstly, the strain measuring position of the small connecting rod is determined by the finite element method. Secondly, the measurement model of hinge moment is established and verified by the off-line load calibration test and the hinge moment on-line verification test. Finally, the flight test results of rudder hinge moment model are obtained through the coordinated sideslip maneuver. The results show that the measured model are accurate and effective, meeting the flight test requirements, which can apply to the measurement of rudder hinge moment with the similar driving structure.

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